柔性翼微型飞行器气动特性的实验研究

 柔性翼有望提高微型飞行器(MAV)的抗风能力。为进一步了解柔性翼的气动性能，建立MAV数学模型，并为飞行仿真和飞行控制设计做准备，在低雷诺数风洞中对柔性翼微型飞行器进行了风洞试验，同时采用翼型、机翼平面形状和尺寸大小均相同的刚性翼进行了风洞对比试验。对比结果表明：柔性翼相比于对应的刚性翼，失速迎角较大；柔性翼的最大升力系数较大,但是柔性翼的变形在提高升力的同时也增大了阻力，升阻比的情况较为复杂；在较低雷诺数情况下，柔性翼的纵向静稳定性略优于刚性翼；柔性翼的长周期和短周期模态的衰减特性和阻尼特性略优于刚性翼。

Experiment Research on Aerodynamics of Flexible Wing MAV

The design of a flexible wing can enhance the capability of gust resistances for a micro air vehicle (MAV). To understand the aerodynamics of the flexible wing and establish a mathematic model for it,experiments on the flexible wing were performed using a low Reynolds number wind tunnel. The established model can be used for flight simulation and control design of the MAV. Comparable experiments with a fixed wing of the same size and shape were also conducted which illustrated distinct aerodynamic advantage...